De-icing system for a fixed or rotary aircraft wing

Abstract

A de-icing system for a fixed or rotary aircraft wing. The system is capable of generating ultrasound that is transmitted at least locally to an outside surface of the wing, wherein the system comprising a base structure ( 2 ) covered at least locally with at least one leading edge ( 3 ), an elastomer structure ( 1 ) arranged and secured between the base structure ( 2 ) and the leading edge ( 3 ), housings ( 4 ) defined in the elastomer structure ( 1 ) and open towards the leading edge ( 3 ), piezoelectric actuators arranged in at least some of the housings ( 4 ) in order to generate ultrasound, wiring ( 10 ) connecting the piezoelectric actuators to an electrical control and power supply unit, and a fastener for fastening the leading edge ( 3 ) onto the base structure ( 2 ) while coming into contact with the piezoelectric actuators ( 4 a ) arranged in their respective housings ( 4 ).

What is claimed is: 
     
       1. A de-icing system for a fixed or rotary aircraft wing, the system being capable of generating ultrasound that is transmitted to an outside surface of the wing, the wing including a base structure covered at least in part by at least one leading edge, the system including:
 piezoelectric actuators; 
 a support structure for the piezoelectric actuators, the support structure being arranged and secured between the base structure and the leading edge, the support structure including cells and being pierced to include empty spaces between the cells, each cell defining a housing that is open towards the leading edge, the piezoelectric actuators being arranged in at least some of the housings in order to generate ultrasound waves that propagate in at least one direction substantially in parallel with the outside surface; 
 wiring connecting the piezoelectric actuators to an electrical control and power supply unit; and 
 fastener means for fastening the leading edge to the base structure and to the piezoelectric actuators. 
 
     
     
       2. A de-icing system according to  claim 1 , wherein the support structure is made of an elastomer. 
     
     
       3. A de-icing system according to  claim 2 , wherein the elastomer support structure comprises a perforated first layer secured to the base structure by means of a polymerizable resin, and a perforated second layer secured to the first layer by connection means of the adhesive film type, the housings for the piezoelectric actuators being provided in the second layer. 
     
     
       4. A de-icing system according to  claim 3 , wherein the cells are connected to one another in the first elastomer layer by elastomer connecting bridges forming integral portions of the first layer. 
     
     
       5. A de-icing system according to  claim 3 , wherein the leading edge is bonded to the second layer of the elastomer structure. 
     
     
       6. A de-icing system according to  claim 1 , wherein the support structure is prestressed to exert forces on the piezoelectric actuators. 
     
     
       7. A de-icing system according to  claim 1 , wherein the support structure, the base structure, and the leading edge are secured to one another using films of adhesive. 
     
     
       8. A de-icing system according to  claim 1 , wherein the cells are structurally independent and are connected to one another by a polymerizable resin and by the leading edge. 
     
     
       9. A de-icing system according to  claim 1 , wherein the cells are hexagonal in shape. 
     
     
       10. A de-icing system according to  claim 1 , wherein the empty spaces between the cells are filled with a polymerizable resin. 
     
     
       11. A de-icing system according to  claim 10 , wherein the leading edge has an inside face presenting projecting studs engaged in the polymerizable resin contained in the empty spaces. 
     
     
       12. A de-icing system according to  claim 1 , wherein the leading edge is made up of one or more portions so as to cover a continuous zone of the wing, or discontinuous zones thereof. 
     
     
       13. A de-icing system according to  claim 1 , wherein the means for fastening the leading edge are adhesive means providing adhesive bonding with the piezoelectric actuators arranged in the housings. 
     
     
       14. A de-icing system according to  claim 1 , wherein the means for fastening the leading edge comprise flexible fastener elements secured to the base structure and made of a material of the neoprene or silicone type, the ends of the leading edge being fastened thereto by adhesive, the base structure presenting a setback in register with the leading edge so as to define an empty gap in which the piezoelectric actuators are arranged. 
     
     
       15. A de-icing system according to  claim 1 , wherein the de-icing system extends under at least a portion of the wing that does not include the leading edge. 
     
     
       16. A de-icing system according to  claim 1 , wherein the wiring is arranged on the wing either in distinct zones when the leading edge has a distinct portion for each of the distinct zones, or overall in a single zone when the leading edge comprises a single piece over the single zone. 
     
     
       17. A de-icing system according to  claim 1 , wherein the piezoelectric actuators are constituted by disk-like ceramic elements presenting a shape that is substantially cylindrical. 
     
     
       18. A fixed or rotary aircraft wing including a de-icing system in accordance with  claim 1 . 
     
     
       19. A blade for a rotorcraft main rotor, the blade including a de-icing system in accordance with  claim 1 . 
     
     
       20. A movable element of an aircraft fixed wing, the element including a de-icing system in accordance with  claim 1 .